Abstract

An unstructured grid generation method, developed for particular application to multi-element, high-lift aerofoil configurations operating at high-Reynolds number conditions, is presented. The grid generation method starts by creating anisotropic triangular computational cells around the aerofoil elements, in order to provide adequate resolution of boundary layer and wake regions. The remainder of the flow domain is then triangulated, using an edge-splitting algorithm that creates new computational cells, grid points and cell connectivities simultaneously. Flow solutions are obtained by solving the Reynolds-averaged Navier-Stokes equations, in conjunction with a differential Reynolds stress turbulence model and wall function boundary conditions. Results for 3-, 4- and 5-element aerofoil configurations are presented and compared with experimental measurements obtained during the UK’s National High Lift Programme of the 1970s.